Flying-machine.



' Patented Feb; 2, 1915.

'! SHEETS-SHEET 1 T. A.'B. LAKE.

FLYING MACHINE.

APPLICATION IILI ID' MAR. 16, 1914.

T. A. E. LAKE.

FLYING MACHINE,

APPLICATION FILED MAR.16.1914

T. A. E. LAKE.

FLYING MACHINE.

A'I'PLIOAIION rum 1.11m 10. 1914 Patented Feb. 2, 1915.

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Patented Feb. 2, 1915.

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wi'lwwomo T. A. E. LAKE. FLYING MACHINE" APPLICATION FILED MAR.16, 1914.

Patented Feb. 2, 1915.

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T. A. E LAKE. FLYING MACHINE APPLICATION FILED MAR.16, 1914.

Patented Feb. 2, 1915.

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APPLIOATION FILED MAR.16,1914.

Patented Feb. 2, 1915.

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THOMAS ALVA EDISON LAKE, 0F MILFORD, CONNECTICUT.

FLYING-MAGI-HNE.

I Specification of Letters Patent.

Patented Feb. 2, 1915.

Application filed March 16, 1914. Serial No. 825,159.

To all whom it may concern:

Be it known that I, THOMAS ALVA EDISON LAKE, a citizen of the United States, residing at Milford, in the county of New Haven and State of- Connecticut, have inventedcertain new and useful Improvements in Flying-Machines, of which the following 15 a specification. v

The object of the invention is to provide a stable even-keel flying machine having a reater factor of safety in straight-away flight when acting under the influence of the propellent force, and in descending in the event of the loss of the propellent force, than has been possible in heavier-than-air machine heretofore constructed.

I attain my results, first, by disposing the center of gravity of the machine as a whole, well below the longitudinal and transverse center of the sustaining planes, below the center of thrust of the propellers, and below the center of forward resistance, and secconstructing the sustaining planes so that they may be bent upwardly at their forward ends and downwardly at their rear ends so that the angle of incidence to the atmosphere wlll cause the machine to rise on an even-keel when the propellent pellent force thereby force is acting,.or so that they may be bent downwardly at their forward ends and upwardly at their rear ends to thus change the angle of incidence to cause the machine to descend on an even-keel when in flight, or so that the forward and rear-ends of the planes may be simultaneously bent either upwardly or downwardly to present concavo-convex surfaces to the passing air currents when making a descent without the aid of the pro- .act as parachutes to check the downward momentum of the machineand thus cause it to land without danger to the occupants or to the machine itself, means being provided for; cushioning the landing, and means'also pro-- vided for adjusting the planes when in flight to vary the degree of curvature and for adjusting them, whereby in descending without the aid ofthe propellent force, to cause the air to impinge against either the convex or cohcave surfaces and thus maintain lateral and fore and aft balance as will be hereinafter'described. I v The invention consists in the peculiar and novel features of construction, combinations and arrangements of parts as will be hereinafter fully described and then claimed.

causing the planes to tion,

presented In the drawings, illustrating the invenin the several figures of which like parts are similarly designated, Figure 1 is a side elevation of my machine.- Fig. 2 is a diagrammatic vertical longitudinal section of the same. Fig. .3 is a diagrammatic plan view illustrating only the after aeroplane in position on their stanchions. Fig. 4 is a transverse section drawn on a larger scale on the line aa of Fig. 2. Fig. 5 is a transverse section drawn through the transmission gear case illustrating the driving gear for operating the propellers. Fig. 6 1s a diagrammatic view illustrating the aeroplane controlling lever and its connection to the aeroplanes. Fig.7 is a vertical transverse section drawn on a larger scale on the line 6-?) of Fig. 6. Fig. 8 is a vertical section drawn on the line 0-0 of Fig. 7 Fig. 9 is a horizontal section drawn on the line eld of Figs. 7 and 8. Fig. 10 is a diagrammatic perspective View illustrating the operating mechanism for the forwardhorizontal rudders and the after vertical rudder. Fig. 11 is a diagrammatic side elevation ofthe amidships section of the boat or base of the machine, illustrating the shockabsorbing wheels and the mechanism for adjusting them into and out of operative-positions. Fig. 12 is a horizontal section drawn through one of the guide tubes for the cables of the shock-absorbing wheels and which are ar- 7 ranged in the sides of the boat. Fig. 13 is a diagrammatic plan of the amidships section of the boat illustrating the lateral control wings. Fig. 14 is a side view of the upper and lower ends of oneof the aeroplane 'stanchions illustrating the guide pulleys for the aeroplane operatlng cables. Fig. 15 is an end View of the upper end of the stanchion. Fig. 16 is a side view of the forward end of the boat illustrating the supporting brackets for the forward stanchions. ig. 17 is a diagrammatic perspective view of the forward end of one of the aeroplanes showing the attachments of the operating cables thereto. Fig. 18 is a diagrammatic view illustrating the connection of the fuel tanks to thecarbureter of the engine. Fig. 19 is a horizontal section drawn through the threeway valve controlling the feeding of the fuel to .the engine. Figs. 20, 21, 22 and '23 are diagrammatic views illustrating the various o The 1, preferably rectangular in cross-section and constructed of flat sides 2, which taper from a point forward of amidships toward each end, a bottom 3, and top 4, the whole being constructed of aluminum or other.

light weight material braced by ribs or frames 5. The boat is divided by transverse partitions 6 into a forward compartment 7 in which is located a fuel tank 8, and a radiator 9, which is connected to the engine 10, through. a pipe 11 as shown, afor- Ward passenger compartment 12, an amidship's engine compartment 13, in which is located the engine 10, a control compartment 14, and an after tank compartment 15, in which is held a fuel tank 16, an extreme after water-tight compartment 17, and an extreme forward water-tight compartment 17. In the upper end of the forward tank compartment 7 directly above the radiator 9 are transversely arranged deflector plates 7 for directing the air against the radiator when the machine is in flight to thus reduce the temperature of the cooling water for the engine as the water circulates through the radiator aswill be readily understood.

The engine 10 is mounted upon a suitable base 18 secured to the bottom of the boat and its power shaft is provided with a clutch 19, (Fig. 2), to which is operatively connected the inner end of a transmission shaft 20 having its outer end journaled in a gear case 21 secured to'the forward side of the transverse partition 6 arranged between the engine and control compartments, the extreme end of the said shaft being extended through the partition and is formed to receive a handle (not shown) forcranking the engine. Mounted on the transmission shaft20 and housed within the gear case is a drive gear 22 which meshes a gear 23 of the same diameter carried by a shaft 24 journaled in the gear case 21, and formed on or connected to each gear is a sprocket wheel 25 (Fig. 5), over which operate sprocket chains 26 which also operate over thus attain greater efliciency since the fricsprocket wheels 27 mounted upon shaft 28 of propellers 29 which shafts 28 are journaled in bearings-30 formed at the vertex of tripods 31 extending outwardly and upwardly from the hull of 'the boat, and within the hull the sprocket chains operate in tubular casings 32 extending from thegear case to the sides of the'hull and which surround the openings in said gear case and the sides of the. hull through which the chains pass. By this arrangement of the gearing for driving the propellers it will be observed that I avoid the necessity of crossing the chains as is the common practice in flying machines using two propellers and tion and consequent wear upon the-chains are avoided. The operation of the clutch 19 is controlled by a foot treadle 32 located in the control compartment and which is operativelyconnected to the clutch in suitable manner..

, The fuel tanks 8 and 16 are connected by a-pipe 33 (Fig. 18) in which is arranged a three-way'valve 34 and from the third way of the valve extends a fuel pipe 35 which is connected to the carbureter '36 of the engine. By the use of the three-way valve it will be evident that by adjusting the valve,

fuel may be supplied to the engine fromv 38, 39, 40 and 41 designate pairs of stanchions extending from the deck of the boat, the intermediate stanchions having their. lower ends extended through the deck .or top 4 and held in suitable sockets 42 (Fig.

4) secured to the inner surfaces of the sides 2, while the forward and rear stanchions have their lower ends fitted in'brackets 43 and 43; respectively, mounted on the top of the. deck. Mounted upon each pair of stanchions, in step-like order throughout the length of the machine and having a slight vertical movement on its stanchions, is-an aeroplane 44, each being constructed of flexible longitudinally arranged ribs 45 (Figs. 6 and 17) which are covered by fabric in the usual manner and each aeroplane is braced to its stanchions by guy wires 46 which are arranged in pairs, each pair extending from a common eye at the top of their stanchion in outwardly and diverging directions through the surfaces of the planes and thence inwardly and convergingly toward the bottom of their stanchion to which theyare connected in suitable manner, the said wires being suitably connected to the ribs of the aeroplanes so as to hold the central portions of the.

aeroplanes rigid for the hereinafter appear.

Control of the vcourse of the machine in vertical directions is effected by bending the forward and rear ends of the aeroplanes upwardly and downwardly' throughout their transverse lengths so asto change the angle of incidence to'the planes and thus cause the machine to descend on an even-"keel. It may be stated here that the aeroplanes have their greatest length extending transversely of the machine, and to effect the above stated adjustments I connect the forward and rear ends of each aeroplane with operating wires purpose as will or cables 47, 47, 47" and 4 as shown most clearly in Figs. 3, 6 and 17. The Wires 47, and 47", extending from the upper surfaces of the planes, operate over guide pulleys 4'8 journaled at the tops of the stanchions, are extended downwardly along the stanchions around guide pulleys 49 and have their ends connected to the opposite ends of a common rocking arm, 50 mounted on a shaft 50" slidingly retained in guide brackets 51 secured to the sides of the boat, while the wires or cables 47 and 47 ex: tending from the lower surfaces of the planes operate over guide pulleys 52 journaled at the base of the stanchionsaround guide pulleys 53 and have their ends also connected to the opposite ends of the said rocking arms 50 as shown most clearly in Fig. 6. To the lower end of one of the rocking arms is pivoted the forward end of a connecting rod 54 having its. rear or opposite end pivoted on a pin 55 carried at the lower end of a control lever 55 which is journaled intermediate its ends on the outer end of a stationary shaft 56 (Figs. 6, 7 and 8-) held in a bracketsecured to one side of the hull of the boat. By this arrangement it will be seen that as the upper end or handle of the lever 55 is moved forwardly as shown in Fig. 20, the lower end of the said lever will be moved in the opposite direction which, through the connecting rod 54, will rock the arms 50 and its shaft todraw the lower end of the said arm rearwardly and move its upper end forwardly, thus pulling upon the wires 47 and 47 to bend the forward ends of the aeroplanes upwardly and their rear ends downwardly andt hus present the lower surfaces of the aeroplanes to the atmosphere to cause the machine to rise when acting under the influence of the pro-' pellent force. It will be obvious that a reverse movement of the control lever will, pull upon the wires 47 and 47 ends of the aeroplanes downwardly and their rear ends upwardly to thus p sent the upper surfaces thereof to the atmosphere to cause the machine to descen on an even-keel when in flight. I 147 and 147 (Figs. 3 and 17), g a bracing cables which extend from the ,I I 1a1I1 operating cables 47 47 :7" and to the outer fore and aft ends of the a'erop so as to bend the entire transverse surfaces of the said aeroplanes evenly when the main As shown the wires or cables are opera main cables of each aeroplaneare extended from the edges thereof to the1r pulleys in substantially parallel relation and the bracii1g -C2lb1.3s are extended outwardly d d dl f their cables to the edges of the said planes thereby bracing the said planes and causing them to be bent uniformly throughout their entire transverse width and to prevent any tendency of the to bend the lanes to twist I connect the main wires or cables at the points of connection of the bracing wires, with cross wires 149 and by diagonally arranged wires 150, which extend from one main wire to the point of connection of its cooperating main wire with the aeroplane.

In order to hold the shaft 50 of the rock ing arms against longitudinal movement when the control lever is operated to bend the forward and rear ends of the aeroplanes, Iprovide the following arrangement: J ournaled-at its upper end upon the shaft 56 is a segmental arm 58 (Figs. 6, 7, 8 and 9), to which is pivoted one end of a connecting rod 59 having its forward end mounted upon the shaft 50 the segmental arm being held against swinging movement 1 on the shaft 56 by a spring actuated locking pin 60 slidingly retained in a boss formed upon the base of the bracket 57, and which has its outer endnormally held in an aperture 61v formed in the lower end of the segment 58. Now in order to simultaneously bend the forward and rear ends of the planes either upwardly or downwardly, I mount the control lever 55 upon its shaft so that it will have a slight lateral movement, and I extend the pin 55 through the. lower end of the lever 55 so that when the upper end of the lever is moved inwardly toward the center of the boat, its lower end will be moved outwardly to thus cause the pin 55 to .push the locking pin 60 from the aperture 61 against the tension of its spring thus unlocking the segmental arm 58 from the bracket and at the same time locking the said arm'to the control lever 55 so as to ea'iise them to swing together as the control lever is operated. By this arrangement it will be apparent that as the control lever is moved inone direction or the other the rocking arm 50 and its shaft will be moved backwardly or forwardly to thus bend the forward and rear ends of the aeroplanes upwardly or downwardly to assume concavo-convex surfaces for the purpose as will be fully understood from the general description of the operation of the machine.

In order to prevent the unlocking ofLthe segmental arm from the bracket, and l1kewise the locking and unlocking of the control lever and the segmental arm, and also to form a guide to prevent lateral movement of the control lever except when the latter is in a vertical position only (with the aeroplanes in horizontal position, bracket with an extension which is-formed with an' upturned flange 62 which prov des a guide for a lip or extension 63 extendmg from the lower end of the control .lever 55, the said flange having a centrally disposed opening 64 through which the lip 63 operates when the said lever ismoved laterally and only when in a vertical-position. By this I provide the control lever is operated with the segmental arm 58 locked to thebracket the lip 63 will ride against the outer face of the flange 62, and thus prevented from being accidentally moved 'in lateral direction and when purposely adjusted to cause the said arm to move with the lever the lip will ride against the inner face of the flange so that the lever and the arm will be held in locked position and caused to move together. 65 designated a locking pawl carried by the control lever and which co-acts with a rack 66 formed on the top of the bracket 57 for locking the lever and its co-acting parts in any position in which they have been adjusted. j

" The brackets 43 of the-forward stanchion are formed with bearings 67 extending from the forward ends thereof providing journals for a rock shaft 68 carrying forward horizontal rudders 68' which extend laterally from the boat and control the trim of the machine in vertical direction, without manipulating the planes to thus correctany tendency the machine might have to dlvert from 'the horizontal keel in striking a sudden gust of wind or air pocket. To one of the rudders is connected a vertical tiller arm 69 to the outer ends of which are connected wires or cables 70 extending from a rocking arm 71 carried at the outer end of a rock shaft wardly and has its forward end connected to the lower end of the arm 73. The shaft 76 is rocked in its bearing by a lever 78 4 (Fig. 10), the upper end of which is formed with forked extensions in the ends of which is journaled a steering wheel 79 havinga peripheral groove in which operates a tiller wire, 80 which is given several turns in the groove of the wheel and which operates over guide pulleys 81 journaled in brackets extending laterally from'the upperend of the lever 78 thence around guide pulleys 82 loosely mounted on the shaft.76 adjacent to the lever, and has its ends connected to the opposite ends of a tiller bar- 83 connected to a vertical rudder 84 mounted on a stanchion or post 84: extending. vertically from the extreme after end of the boat, the

said stanchion being iournaledin a socket 85 secured to the under side of the after of the boat directly a the machine, I provide the sides of the boat with wings 86 (Figs. 1 and 13), substantially triangular in plan and preferably constructed of sheet aluminum, the diagonal edges of the wings being hinged to the sides t-of the propellers with their upper horizontal edges arranged horizontally with respect to the fore and aft trim .of the machine. The wings are operated by lines 87 which are connected to the wings at the top of their vertical edges, the said lines .being extended around guide pulleys 88 carried, at the outer ends of arms 89 extending laterally from the sides of the boat, thence around guide pulleys 90-mounted in the boat, thence around idle pulleys carried at the outer ends of a foot lever 91 journaled intermediate its ends to the hull framing in the bottom of the hull, and have their opposite ends connected to suitable eyes arranged adjacent to the lower guide pulleys 90. By this arrangement should the machine have a tendency to tilt in the lateral direction or when making a turn, the foot lever is operated to move one or the other wing outwardly, as "the case may be, to present a resisting and lifting surface to the atmosphere and thus cause the machine to right itself. ed on the side of the hull and thence for- Journaled in, and extending through the sides of the boat is a rock shaft 92 on the ends of which are mounted triangular frames 93 (Figs. 3 and 11), preferably of Shelby tubing and having parallel or forked members in which are mounted wheels 94- having pneumatic tires. The ends of the shaft 92 are held in the right angle corners of the frames and the wheels in one of the other corners and to the third corners are attached one end of coiled shock-absorbing springs 95 which have their opposite ends to suitable connections inthe boat. Ex-

tending forwardly from the corners of the frames to which the springs are connected are wires or cables 101, which also pass through tubular guides 97 held in the sides of the boat, around guide pulleys 102 thence rearwardly along the sides made fast to the upper ends of'the said arms 99, and from the arms the said wires are continued rearwardly and passed around guide pulleys 103 thence forwardly around guide pulleys carried by said arms adjacent to the pulleys 98, thence rearwardly and downwardly and have their ends made fast to the boat similar to the wires or cables 06. One of the arms is extended beyond the connecting point of the wires or cables and is formed with a handle providing a lever by which the shaft is rocked to move the arms to adjust the cushioning wheels from the position shown in full lines to the position shown in broken lines in Fig. 11. The arm forming the operating lever is provided with a locking dog 10-1 which works over a rack 105 extending from the bottom of the boat. Normally the cushion wheels are positioned below the bottom of the boat and support the weight of the machine when resting on the ground and provide supporting wheels when running over the ground before sufiicient momentum is obtained to lift the machine and they also serve to take up the shock in making a landing as with the use of all similar devices on other machines. However when running over the surface of the water unless some means were provided to lift the wheels out of the water they would afford a drag and retard a rapid rise from the surface but by connecting the frames with the operating wires it will be apparent that should a landing be made on water the wheels may be elevated above the surface thus leaving the machine free to travel over the surface without their resistance and of avoiding a drag when rising. By connecting the operating cables as described it will be understood that when the frames are adjusted from the position shown in full lines to that shown in dotted lines the springs will move along with their wires and frames and thus the necessity of pulling against the tension of the said springs is avoided. However, when adjusted below the bottom of the boat with the operating lever locked to its rack the arms 99 will be prevented from moving so that when the machine strikes the ground or is resting thereon, the frames will pull against the tension of the springs.

106 designates a hydroplane secured at its forward end to the bottom of theboatand having its after end extended slightly'beyond the stern' of the boat and bent upwardly and from the edges of the after end of the boat and resistance, and as of this plane extend uprights 1.07 which fit into the lower ends of the stanchions 11 at the rear end of the machine. The upper ends of the uprights bear against springs (not shown) arranged in the said stanchions whereby to cushion the upward movement of the rear end of the hydroplane.

108 designates a skeg extending vertically from the stern of the boat and has its rear end connected to the stanchion or post 8-1: of the rudder 8%. wind shield or hood arranged over the forward end of the control compartment, and 110 designates seats arranged in said control compartment and the passenger compartment.

As shown the aeroplanes are arranged in step-like order with the forward and after planes on substantially the same level and with the forward and aft transverse edges of the intermdiate aeroplanes out of vertical alinement with each other and out of alinement with the edges of the forward and after aeroplanes. By thus disposing the planes I not only arrange the sustaining surr bility when in straightaway flight and that U in descending no one of the aeroplanes offers interference to any of the other aeroplanes so that without the aid of the propellent influence the machine will descend or drop vertically on an even-keel.

As shown in the drawings, the propellers are'so located that the unit center of their thrust will be as near the unit center (indicated by the reference letters UG on Figs. 1, 3 and 4), of falling and forward far above the center of gravity (indicated by the reference letters *G on Figs. 1 and 4), as practicable construction will permit, so that, in straightaway flight, as when acting'under the ini gravity is provided so that in descending without the aid of the propellers, the boat will serve, as a pendulum-bob and the sustaining planes as a parachute, to thus permit the machine to gradually descend in a 109 designates a vertical direction and on an even keel withv out "danger to the occupants or to the machine itself. p i

In operation we will assume that the ma- 'chine is at rest on the ground. Now to ascend the control lever ismoved forwardly which raises or bends the forward edges of the aeroplanes upwardly and their rear edges downwardly causing them to be adjusted on substantially compound curved lines in, the forward and aft direction of the machine and throughout their entiretinue the angle of incidence is reduced so that only sufficient resisting surfaces are offered to the atmosphere to sustain the machine in the air and to cause it to travel on an even-keel. When thus adjusted the fore and aft trim is maintained by the forward horizontal rudders, their adjustment being controlled by'the lever 78 as will be readily understood. In descending on an even-keel the control lever is drawn backwardly asillustrated in Fig. 21, which adjusts the planes into a reverse position to that for elevating the machine so that it will be caused to. descend on an even-keel. In these adjustments of the aeroplanes it will be noted that the shaft of the rocking arms 50 is held against sliding movement in its bearings 51}, for the purpose as will be hereinafter explained, by means of the connecting rod 59 and the arm 58, which latter is locked to the bracket 57 so that'as the control lever is moved backwardly or forwardly the rocking arm shaft will turn on a pivot,

and when the control lever is thrown back and forth the arm will be caused to oscillate. -As clearly indicated in Figs. 20 and 21, the movement. of the machine in transverse direction will, of course, be controlled ,by the after vertical rudder. In descending when. in straight-away flight, or in banking when making a turn, the machine is apt to cant laterally and in the direction the turn isbcing made, and to avoid excessive and dangerous lateral inclination I provide the machine with wings which are pivoted to the sides of the boat directly aft of the propellers and as near-the center of gravity as it is practicable to arrange them. These wings normally lie fiatagainstthe sides of the boat when the machine is in straightaway flight, but in making a turn should the machine cant the operator pushes one end of the foot lever forwardly which draws one of the wings outwardly from against the'side of the boat to thus offer resistance to the passing air currents to check the downward movement or inclination of that side of the machine. Thus it will be seen that in straight-away flight and in ascending and descending the machine is maintained on an even-keel or in horizontal po sition both longitudinal and laterally. In descending, however, without the aid of the propellent force, the operator brings the control lever 55 to a vertical position in which it will be understood, the aeroplanes are also adjusted to assume a horizontal position, then by throwing the upper end of the control lever inwardly the lower end thereof will be thrown outwardly so that the lip 63 will be passed through the open slot 64 in the guide bracket 'or plate, and this movement will push the locking pin 60 from engagement with the segmentalarm 58 and thus disengage the latter from the bracket and permitting it to move with the control lever 55 as the latter is operated. Now as the control lever is moved, either hackwardly or forwardly, the shaft 51 and its rocking arms 50 will be caused to'move backwardly or forwardly with the said arms held in a vertical position, it being understood that as the pull of the cables on each end of the said arms is equal the latter will maintain a vertical position, and as the said control lever is pushed forwardly, for example, the-arms. will be drawn rearwardly to thus draw upon the cables 47 and 47 to simultaneously bend or curve the forward and rearward edges of the planes upwardly so that they will, assume a substantial trough-shape or concavo-conv'exposition in which position the passing air currents will impinge against the convex surfaces to perinit the machine to descend on an evenkee It is not desirable to constantly maintain the above position of the planes during the entire descending period since, it will be apparent as the air is permitted to escape'past the forward and rear edges of the aeroplanes'very rapidly the machine would descend at increasing speeds, and to check the downward momentum the control lever is drawn, backwardly so that the arms 50 will be moved to the extreme forwardly position which pulls upon cables or wires 47 and 47 to thus draw the forward and rear edges of the aeroplanes downwardly and re versing the curvature thereof and, causing them to assume inverted trough-shape or concave-convex position so that they will serve somewhat in the manner of parachutes, forming, as it were, pockets in which the passing air currents are permitted to escape only at the ends of the planes. However, it is not desirable to maintain the aeroplane in the latter position since the machine would be apt to tilt laterally and once the aeroplanes assume an acute angle in trans verse direction the resisting force would be reduced with the possibledanger of descendthe curvature of the planes fromthe troughshape to the inverted trough-shape-position to not only maintain lateral balance but to check the downward momentum, it being understood, that when the machine gains ex- Y cessive momentum through the planes being curved upwardly the operator throws the control lever to the extreme opposite position so as to cause the aeroplanes to assume inverted trough-shapes and then when the downward momentum has been checked he again adjusts the planes so that the forward and rear ends will be bent upwardly.

From the foregoing it will be seen that I provide an extremely simple, stable and easily controllable machine, one in which the supporting surfaces are equally distributed throughout the length of the machine one in which the fore and aft and lateral stability both in flight. and descending without the aid of the propellent force is at all times maintained which is a great factor as it permits a safe landing in the event of accident to the engine or lack of fuel, and one in which the aeroplanesmay be quickly adjusted to change the angle of incidence whereby the machine is caused to ascend, or descend on an even-keel While in flight.

Of course, it will be understood that in practice the stanchions will be braced to the boat or car and to each other by guy wires to provide a thoroughly rigid structure. These wires are indicated by the reference numeral 120,, and while not shown, it will also be understood that the main operating wires or cables 47, 47, 47" and 47 of all of the aeroplanes will be extended over suitably located pulleys and connected to the arms 50 in similar manner as shown in Fig. 6, so that all of the aeroplanes will be simultaneously operated by the operation of the one control lever 55.

What I claim is 1. In a flying machine, a base, a plurality'of flexible aeroplanes supported above the base, theforward and after aeroplanes being disposed in substantially the same horizontal plane, and means for bending the forward and rear ends of said aeroplanes upwardly or downwardly in opposite directions or in the same direction while the machine is in flight.

2. In a flying machine, a plurality of flexible aeroplanes arranged in step-like order and so disposed that no one of said. aeroplanes offers resistance to its adjacent aeroplane when descending .onan evenkeel, and manually operated means for bending the forward and rear ends of said aeroplanes upwardly or downwardly throughout their transverse length while the machine is in flight, for the purposes specified. I 3. In a flying machine, a plurality ,of flexible aeroplanes arranged in step-like order, the forward and after aeroplanes being disposed in substantially the same horizontal plane, and means operatively connected to the forward and rear ends of said aeroplanes forvbending them upwardly'or downwardly in opposite directions or in the same direction while the machine is in flight.

4. In a flying machine, a plurality of flexible aeroplanes or sustaining surfaces arranged in step-like order, a base arranged below the aeroplanes or supportlng surfaces, and manually operated means for simultaneously bending the forward and rear ends of the said aeroplanes or supporting surfaces upwardly or downwardly, in

for the purposes specified.

5. In a flying machine, a base, a flexible aeroplane mounted above the base, means for bending the forward and after ends of said aeroplane upwardly or downwardly in opposite directions, and ugeans co-acting with the first mentioned means 'for bending the forward and after ends of said aeroplanes upwardly or downwardly in the same direction, said means being operable while the machine is in flight, for the purposes specified.

6. In a flying machine, a plurality ,-of flexible aeroplanes, means operatively connected to said aeroplanes for simultaneously bending the forward and rear ends thereof upwardly or downwardly in opposite directions, and means co-acting with said operating means for bending the forward and rear ends of saidaeroplanes upwardly or downwardly in the same direction. Q

7. In a flying machine, the combination with a base, of a plurality of flexible aeroplanes or supporting surfaces arranged above the base in step-like order, said aeroplanes or supporting surfaces being disposed so that no plane will offer resistance to the other when the machine is descending vertically on an even-keel, and positively operated means for simultaneously bending the forward and rear ends of said aeroplanes upwardly or downwardly in opposite directions for the purposes specified.

8. In a flying machine, the combination $5 opposite directions or in the same direction,

with a base, of a plurality of aeroplanes or supporting surfaces arranged above the base in step-like order, said aeroplanes or supporting surfaces being disposed so that no plane will offer resistance to the other when the machine is descending vertically on an even-keel, means for bending the forward-and rear ends of the said aeroplanes upwardly or downwardly in opposite directions or in the same direction while in flight for the purposes specified, a horizontal trimming rudder mounted at the end of said base, and a vertical steering rudder mounted at the after end of said base. 7

9. In a flying machine, the combination with abase, of a plurality of flexible aeroplanes supported above the base, and means for bending the forward and rear edges of said aeroplanes upwardly or downwardly in opposite directions throughout their transverse length while in flight to present either the upper or lower surfaces to the atmosphere, for the purposes specified.

10. In a flying machine, the combination with a base, of a plurality of flexible areoplanes arranged in step-like order above the said base and out of vertical alinement, for the purposes specified, and means operable.

from said base for bending the forward and rear ends of said aeroplanes upwardly or downwardly in opposite directions or in the same direction, substantially as and for the purposes specified.

11. In a flying machine, the combination with a'base, of a plurality of stanchions ex-- tending therefrom, flexible aeroplanes or sustaining surfaces mounted on 'said stanchions, means operable from within the base for bending the forward and rear ends of said aeroplanes upwardly or downwardly, as specified, a forward trimming rudder, an after lateral steering rudder, and stabilizing wings connected to said base.

12. In a flying machine, a flexible supporting surface, and means for bending the forward and, rear ends of said supporting surface upwardly and downwardly in the same direction or in opposite directions.

13. In a flying machine, the combination with a base, of a plurality of flexible aeroplanes mounted above the base in step-like order, and a control lever -operatively connected to said aeroplanes for bending the" forward and'rear ends thereof upwardly or downwardly in opposite directions throughout width and for changing the angles of incidence of said aeroplanes.

14.1 In a flying machine, the combination with a base, of a plurality of flexible aeroplanes mounted above the base and adapted to be bent upwardly and downwardly at their forward and rear ends in opposite dimotions and a control lever operatively connected to said aeroplanes for so bending them and for changing their angles of incidence throughout their entire width, forward trimming rudder and an after steering rudder and means for operating the \said rudders.

15'. In'a' flying machine, the combination with a base, of a plurality of flexible aeroplanes mounted above the base in step-like order and out of vertical alinement, a control lever operatively connected to said aeroplanes for changing their angle of incidence in straightaway flight and for bending said planes mounted above the base in step-like order, a control lever operatively connected to said aeroplanes for bending their forward and rear edges upwardly or downwardly to change their angles of incidence to cause the machine to ascend or descend on an evenkeel, trimming rudders mounted at the forward end of the. base, a steering'rudder mounted on the after end of the base, means for operating said trimming and steering rudders, and lateral control wings mounted on the sides of the base:

17. In a flying machine, the combination with a base, of stanchions arranged in pairs extending from the base, aeroplanes supported by said stanchions and arranged in step-like order, propellers supported at the sides of the base and having their centers of thrust arranged substantially at the center of forward resistance and above the center of gravity of the machine, means for operating the propellers, forward trimming rudmounted in the control compartment for bending the forward and rear ends of said aeroplanes, as and for the purposes specified, tripods extending from the base, propellers journaled in the apices of the tripods,

an engine mounted in sald engine compartment andoperatively geared to'said propellers, forward control rudders mounted on -he base, an after steering rudder mounted on the. base, and means for operating said control rudders and said steering rudder.

19. In a flying machine, the combination with a boat constituting the base of the machine, said boat having a plurality of transverse partitions dividing it into a forward passenger compartment and amidships en gme and control compartments and forward and after air and water-tight compartments, of a plurality of aeroplanes mounted above the base in step=lile order, a single control lever mounted in the control compartment andoperatively connected to the forward and rear'ends of the aeroplanes for bending the said ends for the purposes specified, shock-absorbing wheels mounted on the sides of the base and means operable from the control compartment for adjusting said shock-absorbing wheels into and out of operative position, propellers mounted on the 'base above and in transverse vertical alinement with the center of gravity of the machine, an engine arranged in said 'compartmam and operatively geared to said pro pellers, an after steering rudder mounted on the base, lateral stablizing wings mounted on the base aft of the propellers, and independent-means for operating the said 'steering rudder and said stablizing win'g's.

20; In a 'flying machine, the combination with a boat constituting the base of the fmachine, said boatbeing rectangular in cross section and having a plurality of transverse partitions providing an amidships engine compartment and a control compartment, a plurality of flexible aeroplanes .mounted above the base in step-like order, a single control "lever mounted in the control compart'ment and operatively connected to all of said aeroplanes for bending their forward and rear edges upwardly or downw'ardly for the purposes specified, tripods extending from the base, propellers Journaled in the apices of said tripods, an en-' gine mounted in said compartment and op eratively geared to saidpropellers, 'a fuel tank arranged in the forward and after ends of the base, means connecting the tank for supplying fuel oil to the engine and for conducting the fuel from one tank to the other, and means controlling the admission of'the fuel to the engine and to and from said tanks.

21. In a flying machine, the combination with 'a base of a plurality of flexible we planes mounted above the base in step-like mounted on said stanchions in step-like order, a control lever operatively connected to said aeroplanes for bending their forward and rear ends upwardly or downwardly in opposite directions, and means 60- acting with said control lever for bending the forward and rear ends of said aeroplanes upplane, means operatively connected to the planes for bending their forward and rear' "edges upwardly or'downwardly in opposite "directions, means co-acting with said first mentioned means for bending the forward control wings mounted at the sides of the base, means for operating said Wings, a steering rudder, and means for operating said rudder.

In a flying machine, the combination with a base, of aplurality of flexible aeroplanes mounted above the base in step-like order and out of vertical alinement, propellers supported by the base having their unit center ofthru'st arranged substantially at the unit center of forward resistance and above the center of gravity of the machine, means for operating the propellers, lateral stabilizing wings, forward trimming rud ders, an after vertical rudder, and independent means for operating said rudders.

25. In a flying machine, the combination with a base, ofa plurality of flexible aeroplanes mounted above the base in step-like forder, a control lever operatively connected with said aeroplanes for bending their forward and rear edges upwardly or downwardly 1n opposite dlrectioii, means co-actand rear ends of the planes upwardly or downwardly in the same direction, lateral ing with said control lever for bending their A forward and rear edges upwardly or downwardly in the same direction, trimming rudders mounted at the forward end of the base, a vertical rudder mounted at the after end of the base, means for operating said trimming and vertical rudders, and lateral stabilizing wings mounted at the sides of the base, and means for operating said stabili'zin wings.

26. n a flying machine, the combination with a boat constituting the base of the machine, stanchions arranged at the forward and after ends of the base, flexible. aeroplanes mounted on said stanchions, said aeroplanes being on substantially the same hdrizontal planes, intermediate stanchions extending from the base and having aeroplanes mounted thereon in step-like order and above said forward and after plane's, a single control lever mounted in the base and operatively connected to all of said aeroplanes for bendingtheir forward and rear edges upwardly or downwardly in opposite direction, means co-acting with said control lever for simultaneously bending the forward and rear edges of the aeroplanes upwardly or downwardly in the same direction, propellers mounted on the sldes. of the base, an engine mounted in the base for op crating said propellers, a vertically mounted steering rudder, and means for operatlng said rudder. I I 27. In a flying machine, the combination with a base, of a plurality of flex ble aerpplanes mounted above the base, operating wires connected to the: forward and rear ends of said aeroplanes and extending upwardly and downwardly therefrom and having their ends connected to arms carried by a single shaft mounted in the base, said. shaft having a sliding and rocking movement, means for locking said shaft against sliding movement, and a control lever operatively connected to one of said arms for rocking said shaft and its arms to bend the .nds of said aeroplanes upwardly or down Wardly in opposite directions, said control lever being adapted to release said locking means and to cause said means to operate therewith to move the shaft and its arms forwardly and rearwardly whereby to bend both ends of the said aeroplanes upwardly or downwardlyin the same ,direction, substantially as specified.

28. In a flying machine, a base, a plurality of flexible aeroplanes arranged in steplike order with the forward and rear aero-, planes arranged on substantially the-same level, operating wiresconnected to the forward and rear ends of said aeroplanes and extending upwardly and downwardly therefrom, a rock-shaft slidingly mounted in the base and having arms to which the ends of said wings are connected, a bracket mounted in the base, a control lever journaled on said bracket and operatively connected with the above said arms for rocln'ng said shaft and its arms to bend the ends of the aeroplanes upwardly or downwardly in opposite directions, a segmental arm journaled in said bracket, a connecting rod connecting said segmental arm with said shaft, a'spring actuated locking pin carried by said bracket and adapted to engage and lock said segmental arm against ,movement, and a pin carried by said control lever for engagement ,with said locking pin to unlock said segmental arm from said bracket and to connect it with said control lever whereby to slide the shaft and its arms forwardly and changing'theirangles of incidence and for varying the degrees of curvature 'of,said

aeroplanes whenin flight. g

30. In 'aiflying machine, a base, a plurality of aeroplanes mounted above the base in step-like order and out of vertical alinement, propellers mounted on thee sides of the base, an engine operatively l 'geared to said propellers: fuel tanks arranged forward andaft of the longitudinal center of the base, means to supply fuel to the engine from such tanks,.and means for transferring the fuelfrom one tank to the other whereby-- to maintain the desired center of gravity and for compensating for the disposal of weight carried in the base.

. 31. In a flying machine, a base, aflexible aeroplane supported abovethe base, means mounted in the base and operatively connected with the forward and rear edges of said aeroplane for bending said edges upwardly or downwardly in the same direction and in opposite directions to change its angle of incidence and for varying the de- 'grees of curvature thereof throughout its' transverse length, -'shock absorbing wheels mounted on the sides of the base forward of the longitudinal center thereof, and a shock-v absorbing skid arranged at the after end of the base. 7 1

32. a flying machine, a boat constituting the base of the machine, a flexible aeroplane'mounted above they base, a control lever mounted inthe base and operatively connected to the forward and rear edges of said aeroplane for bending them upwardly or downwardly in opposite directions to change its angle of incidence and for vary ing the degrees of curvature, means co-act ing with said lever to bend the forward and rear edges of the aeroplane upwardly or downwardly in the same direction for the purpose specified, shock-absorbing wheelsadjustably mounted'on the sides of the base, means for adjusting said wheels into and out of operative position, a yielding skidmounted on the bottom of the base at the after end thereof, forward trimming rudders',.an after lateral steering rudder, and means for operating said rudders.

- 33. In a flying machine, a base, a flexible aeroplane supported above the base, and means mounted in the base and operatively connected with the forward and rear ends of said aeroplane for bending said ends upwardly or downwardly in opposite directions to change its angle of incidence and for varying the degrees of curvature of said aeroplanes and means coacting with the said first mentioned means for bending said dlrection.

34:. A flying machine, of adjustable supporting ends upwardly or downwardly in the same having a plurality surfaces or planes,

and aft ends of the a base,.-prepellers mounted on the base, an engine operatively fuel-holding tanks arranged in the forward base and connected to the engine, and means for controlling the supply of fuel to the engine" from either tank individually or from both tanks simultaneously.

35. A flying-machine, provided with fuelholding tanks for the engine, said tanks being located forward and aft of the longituboat and connected tothe-engine, means for directing currents of air against the radigeared to the propellers,

ator while the machine isin flight, andpropellers operatively. connected with the en- '1ne. v a 37. In a flying-machine, a boat constituting the base of the machine, an engine arranged in the boat, fuel-holding tanks ar ranged in the boat forward and aft of the engine and connected thereto, as specified, a cooling-water radiator arranged in the bow of the boat and connected to the engine, and deflectors arranged in the boat above said radiator adapted for directing currents of air against the said radiator when the -machine 1s in flight.

In testimony whereof I have hereunto set my hand this 13th day of March, A. D. 1914.

THOMAS'ALVA EDISON LAKE.

Witnesses; v v

F. B. WmTNnY, E. G. GALLAGHER. 

